US6082096A - Turbo-jet engine thrust-reverser fitted with scoop-doors linked to a movable cascade - Google Patents

Turbo-jet engine thrust-reverser fitted with scoop-doors linked to a movable cascade Download PDF

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Publication number
US6082096A
US6082096A US09/265,973 US26597399A US6082096A US 6082096 A US6082096 A US 6082096A US 26597399 A US26597399 A US 26597399A US 6082096 A US6082096 A US 6082096A
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United States
Prior art keywords
door
thrust
cascade
pivot
upstream
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Expired - Fee Related
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US09/265,973
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English (en)
Inventor
Guy Bernard Vauchel
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Safran Nacelles SAS
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Hispano Suiza Aerostructures
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Assigned to HISPANO SUIZA AEROSTRUCTURES reassignment HISPANO SUIZA AEROSTRUCTURES ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: VAUCHEL, GUY BERNARD
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing

Definitions

  • the present invention relates to a bypass turbo-jet engine thrust reverser having a scoop-type door and at least one movable cascade.
  • a turbojet engine is fitted with a duct 17 consisting of an inner wall enclosing the actual engine structure and an outer wall which is continuous with the engine cowling enclosing the fan.
  • This outer wall is able to simultaneously channel the bypass flow and the primary flow to the rear of the exhaust of the so-called hot, primary flow as regards a mixed- or confluent-flow, but in other cases the outer wall may only channel the bypass flow as regards a separate flow.
  • a wall may fair the outside of the casing enclosing the outside of the outer wall of the above described duct, namely for the purpose of minimizing powerplant drag. This is especially the case for powerplants which project from the aircraft, in particular when such powerplants are mounted under the wings or at the rear of the fuselage.
  • European patent document EP 0,822,327 A discloses an illustrative embodiment, shown in FIG. 1 of the attached drawings, of a scoop-door thrust-reverser used in a bypass turbojet engine.
  • the thrust reverser consists of a movable sub-assembly and a stationary structure.
  • the movable sub-assembly consists of a hollow door 3 forming a movable portion 2 and constituting, when in the forward-thrust mode, part of the external cowling.
  • the stationary structure consists of an upstream portion 6 upstream of the door 3, a downstream portion 7 downstream of the door 3, and beams linking the upstream portion 6 to the downstream portion 7, the stationary structure also being part of the external cowling.
  • At least one door 3 is mounted along a circumference on the external cowling and is pivotable, in a downstream portion of its side walls, on the beams, situated on each side of the door, linking the downstream portion 7 to the upstream portion 6 of the external cowling.
  • the side walls connect the external part, i.e., the outer panel 4 of the door 3, which constitutes a part of the external cowling, to an inner part 5 of the door 3, which constitutes a part of the outer wall of the duct.
  • the stationary-structure's upstream portion 6 comprises a forward frame 8 which may be used as a rest for a control means to displace the door 3, for instance linear actuators.
  • This displacement control means for the door 3 may also be situated elsewhere on the periphery of the door 3, for instance downstream of it. In the latter case, the stationary structure's downstream portion 7 shall serve as the rest for the control means.
  • the door 3 When driven toward an open position, the door 3 tips in such manner that the door portion upstream of a door pivot 9 more or less completely obstructs the duct 17 while clearing a passage in the external cowling to allow flows 13 and 14 to be channeled in a centrifugal direction relative to the duct axis, on one hand into an inner duct or conduit 10 constituted by the structure of the door 3, and on the other hand between a deflecting edge of the stationary structure and the outer panel 4 of the door 3.
  • the door's downstream part is thereby moved into the vicinity of the outside of the external cowling.
  • the door's pivot angle is adjusted in such manner so as to allow exhausting of the flow so as to strongly reduce, even suppress, the forward thrust of the flow, and to generate a counter-thrust by generating an upstream-directed flow component 13b.
  • the outer panel 4 of the door 3 of the above described thrust reverser model comprises an exhaust path for flow 14 between the deflection edge and the outer surface of the panel 14.
  • the flow 14 meets the flow 13b exhausting from the door's inner duct 10. By merging with this flow 13b, the flow 14 minimizes the forward direction assumed by the flow 13b.
  • French patent application 97.06943 solves this problem by using a movable baffle 5 positioned above the outer panel of the door 3 when the door opens so as to limit, or restrict any interference between the door's exhaust flow and the flow deflected by the door's outer panel.
  • FIG. 2 shows an embodiment of this invention in the thrust-reversal position.
  • baffle 5 For reasons of seating and kinematics, the sort of baffle 5 described in French patent application 97.06943 will partly or totally cover the cascade vanes in the forward-thrust mode.
  • at least the downstream part of the baffle starts from a blade-straddling position 5a and moves toward a position 5b in which it covers the door's outer panel 4.
  • an exhaust aperture 15 for the door's flow 13 cannot be completely freed and thus cannot allow free thrust-reversal flow transmission. Consequently, performance problems may arise in the turbojet engine because the cross-section of the annular duct 17 obstructed by the door 3 might not be compensated by the flow-transmitting cross-section freed by the door.
  • the forward-thrust positioning of the baffle does not allow, or only with great difficulty, the optimal shape, as desired by expert, of the baffle 5.
  • a sealing means 12 between the downstream zone of the baffle 5 and the outer panel 4 may entail some performance degradation due to part of the flow moving above the outer panel 4 toward the flow exhausting from the door 3.
  • the baffle 5 is driven by a linkage system mounted outside the sides of the door 3 and secured to the door.
  • the guidance technique using four linkrods entails a multiplicity of drive parts and requires rigorous manufacture to attain the reliability required of the thrust reverser.
  • the configuration of the stationary vanes is designed to secure optimal thrust-reversal performance. It is impossible to direct the flow forward in the manner considered optimal by expert during opening of the door 3.
  • One objective of the invention is to attain enhanced aerodynamic performance of the scoop door when in the reverse-thrust mode, and particularly during opening, without incurring the drawbacks of the known prior art.
  • turbojet-engine thrust-reverser fitted with one or more scoop doors of the above described kind, wherein each door is combined with at least one movable deflecting cascade hinging about a pivot.
  • An upstream portion of the cascade forms a deflector that projects beyond an outer surface of the door's outer panel when the door is in the open position so that all interference between the door's exhaust flow and the flow deflected outside the door is avoided.
  • the cascade mobility allows the vanes of the cascade to be oriented farther upstream than at the end of the opening operation. Consequently, that cross-section of the flow crossing the door structure is optimally guided, and because the direction of flow points less at the stationary fairing part covering the door's exhaust so as to create a plug effect, the aerodynamic efficacy of the thrust-reverser is improved;
  • FIG. 1 is a semi-diagrammatic longitudinal section, in a plane through an axis of rotation of an associated turbojet engine, of a thrust reverser, fitted with pivoting scoop doors in an open position, of a known model and already described above;
  • FIG. 2 is a view similar to that of FIG. 1 of a thrust reverser, fitted with scoop doors comprising a movable baffle, of a known type and already described above;
  • FIGS. 3, 4 are perspective views of the present invention shown in FIGS. 5 through 7;
  • FIG. 5 is a view similar to that of FIG. 1 for the closed position of a thrust reverser according to the present invention
  • FIG. 6 is the embodiment of invention shown in FIG. 5 for the open position
  • FIG. 7 is the embodiment shown in FIG. 5 when in an intermediate position
  • FIG. 8 is a view similar to that of FIG. 1 for the closed position of a thrust reverser according to another embodiment of the invention.
  • FIG. 9 is the embodiment shown in FIG. 8 for the open position
  • FIG. 10 is a view similar to that of FIG. 1 for the closed position of a thrust reverser according to yet another embodiment of the invention.
  • FIG. 11 is the embodiment shown in FIG. 10 for the open position.
  • a scoop door 3 of a bypass turbojet-engine thrust-reverser hinges about a door pivot shaft 9 resting on side beams of the thrust-reverser's stationary structure 6.
  • a control system 19 of the door 3 drives a movable cascade 23, at a cascade drive point 21 and a cascade pivot point 22, the movable cascade 23 being hinged on a cascade pivot shaft 24 resting on the inner structure of the door 3.
  • the movable cascade 23 is situated inside the structure of the door 3, and the upstream portion of the stationary fairing 16 interfaces with the downstream end of an outer panel 4 of the door 3.
  • the movable cascade 23 includes a plurality of vanes 25 of which an upstream portion forms a deflector 26 for exhaust flow during thrust reversal.
  • control system or linear actuator 19 drives, at a door drive point 18, the door 3 into rotation about the door pivot shaft 9 and simultaneously begins to operate the linkrod 20 at cascade pivot point 22.
  • linkrod 20 acting on cascade drive point 21, drives the movable cascade 23 into rotation about cascade pivot shaft 24 as far as a position determinable by the expert.
  • a suitably shaped extension on an upstream portion of the deflector 26 takes into account the play between the two moving parts.
  • the design of the extension of the deflector 26 may be used to form a stop against the outer panel 4 of the door 3 for the movable cascade 23 when in the thrust-reversal mode. This is particularly useful when the design of the vanes 25 allows driving and positioning of the cascade 23 solely by aerodynamic forces exerted on the structures of the vanes 25 by the deflected flow. An automatic return system may be added to such a design for greater operational reliability when closing the door 3.
  • the deflector 26 moves from an inner inactive position to an outer active one.
  • a space 28 is created between the upstream part of the deflector 26 and a downstream edge 27 of the outer panel 4 of the door 3.
  • the thickness of the deflector 26 and the design of the downstream edge 27 may be designed to increase the space 28.
  • FIGS. 8 and 9 show an embodiment of the invention with a particular design of the deflector 26.
  • One way of increasing the useful height of the deflector 26 during thrust-reversal is to move an outer surface 30 of the deflector 26 into contact with the surface of the cowling, the outer surface 30 of the deflector 26 then becoming part of the aerodynamic lines of the cowling.
  • an upstream portion of an upstream vane 31 assumes the position of the outer surface of the deflector 26 next to the outer panel 4 of the door 3.
  • This configuration moreover allows one to increase an exhaust cross-section 15 at the upstream side by the extension of the deflector 26 without elongating the upstream portion of the fairing 16, thereby avoiding obstructing part of the downstream exhaust cross-section of the door's exhaust cross-section 15 when in the thrust-reversal mode.
  • the extension of the deflector 26 may comprise at least one aperture 32 or an aperture combined with at least one upstream vane 31 to orient a part of the thrust-reversal flow crossing the aperture 32 in a desired direction.
  • This aperture 32 may radially spread from one side edge to the other of the deflector 26.
  • the aperture 32 may be partial in several segments, radially configured, as in this embodiment, or longitudinally configured.
  • the part of the deflector 26 acting as a baffle against the flow also may be fitted with the same contrivances.
  • FIGS. 10 and 11 show an embodiment of the invention wherein a cascade pivot shaft 35 is situated upstream of the door pivot shaft 9 of the door 3.
  • the cascade pivot shaft 35 is located inside the inner door structure.
  • the cascade pivot shaft 35 is situated in an intermediate position of the width of the movable cascade 23.
  • This pivot may be mounted on structurally reinforcing or flow-deflecting walls contained in the inner structure of the door 3, the walls having been defined in the previously described thrust-reverser fitted with scoop-doors.
  • the door 3 furthermore may comprise a stationary cascade-structure portion cooperating with the movable cascade 23 to ensure the desired guiding and deflecting of the thrust-reversal flow.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US09/265,973 1998-03-12 1999-03-11 Turbo-jet engine thrust-reverser fitted with scoop-doors linked to a movable cascade Expired - Fee Related US6082096A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9803035A FR2776023B1 (fr) 1998-03-12 1998-03-12 Inverseur de poussee de turboreacteur a portes formant ecopes associees a une grille mobile
FR98.03035 1998-03-12

Publications (1)

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US6082096A true US6082096A (en) 2000-07-04

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Country Status (6)

Country Link
US (1) US6082096A (de)
EP (1) EP0942165A1 (de)
JP (1) JPH11294260A (de)
CA (1) CA2265230A1 (de)
FR (1) FR2776023B1 (de)
WO (1) WO1999046498A1 (de)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6151886A (en) * 1998-04-02 2000-11-28 Hispano Suiza Aerostructures Turbo jet-engine thrust reverser with scoop doors linked to a displaceable external cowling panel
US20040149861A1 (en) * 2001-06-06 2004-08-05 Strobl William Charles S & H Cycle Engine
US20040195443A1 (en) * 2003-02-21 2004-10-07 Jean-Pierre Lair Self stowing thrust reverser
US20080134664A1 (en) * 2006-12-06 2008-06-12 Spirit Aerosystems, Inc. Thrust reverser pin lock
US20090314887A1 (en) * 2008-06-23 2009-12-24 Rohr, Inc. Thrust reverser cascade assembly and aft cascade ring with flow deflector portion
US7735778B2 (en) 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US20120023900A1 (en) * 2010-07-20 2012-02-02 Airbus Operations (S.A.S.) Aircraft nacelle
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
CN103047048A (zh) * 2011-10-13 2013-04-17 罗尔股份有限公司 具有流向偏转架的反向推力装置叶栅组件
US20140027536A1 (en) * 2012-07-24 2014-01-30 Rohr, Inc. Translating cascades
CN103827473A (zh) * 2011-09-29 2014-05-28 埃尔塞乐公司 带有侧面开口的推力反向器门
US20140150403A1 (en) * 2012-11-30 2014-06-05 General Electric Company Thrust reverser system with translating-rotating cascade and method of operation
US8925295B2 (en) 2010-09-23 2015-01-06 Airbus Operations Air discharging device for an aircraft double-flow turbine engine
US20160160799A1 (en) * 2014-11-06 2016-06-09 Rohr, Inc. Split sleeve hidden door thrust reverser
CN103047048B (zh) * 2011-10-13 2016-11-30 罗尔股份有限公司 具有流向偏转架的反向推力装置叶栅组件
US20170198659A1 (en) * 2016-01-13 2017-07-13 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10343786B2 (en) * 2017-06-28 2019-07-09 General Electric Company System and method of operating a ducted fan propulsion system during aircraft taxi
US10995701B2 (en) 2019-09-05 2021-05-04 Rohr, Inc. Translating sleeve thrust reverser assembly
US11230994B2 (en) * 2017-07-26 2022-01-25 Short Brothers Plc Nacelle with thrust reverser

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6712201B1 (en) 1998-03-13 2004-03-30 Sealed Air Corporation Foam in bag packaging system and method for producing the same
FR2903454B1 (fr) * 2006-07-05 2008-08-29 Airbus France Sas Nacelle de reacteur d'aeronef et aeronef comprenant une telle nacelle
US8006844B2 (en) 2007-09-21 2011-08-30 Ivex Protective Packaging, Inc. Packaging system for producing a foam-in-bag and method of mixing foam

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR822327A (fr) * 1937-05-27 1937-12-28 Perfectionnements aux rouleaux ou paquets de papier hygiénique ou de toilette
US3475913A (en) * 1966-06-29 1969-11-04 Rolls Royce Fluid flow reversers
US4858430A (en) * 1987-07-29 1989-08-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Thrust reverser for a turbofan engine
US5396762A (en) * 1992-12-04 1995-03-14 Societe De Construction Des Avions Hurel-Dubois Thrust reversal assembly for controlling sidewardly diverted flow
US5671598A (en) * 1995-09-13 1997-09-30 Societe De Construction Des Avions Hurel-Dubois Forward mounted pivoting door reverser with efflux control device
US5983625A (en) * 1996-08-01 1999-11-16 Societe Hispano-Suiza Pivoting door thrust reverser with deflecting passage within the door

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR822327A (fr) * 1937-05-27 1937-12-28 Perfectionnements aux rouleaux ou paquets de papier hygiénique ou de toilette
US3475913A (en) * 1966-06-29 1969-11-04 Rolls Royce Fluid flow reversers
US4858430A (en) * 1987-07-29 1989-08-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Thrust reverser for a turbofan engine
US5396762A (en) * 1992-12-04 1995-03-14 Societe De Construction Des Avions Hurel-Dubois Thrust reversal assembly for controlling sidewardly diverted flow
US5671598A (en) * 1995-09-13 1997-09-30 Societe De Construction Des Avions Hurel-Dubois Forward mounted pivoting door reverser with efflux control device
US5983625A (en) * 1996-08-01 1999-11-16 Societe Hispano-Suiza Pivoting door thrust reverser with deflecting passage within the door

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6151886A (en) * 1998-04-02 2000-11-28 Hispano Suiza Aerostructures Turbo jet-engine thrust reverser with scoop doors linked to a displaceable external cowling panel
US20040149861A1 (en) * 2001-06-06 2004-08-05 Strobl William Charles S & H Cycle Engine
US20040195443A1 (en) * 2003-02-21 2004-10-07 Jean-Pierre Lair Self stowing thrust reverser
US6845946B2 (en) * 2003-02-21 2005-01-25 The Nordam Group, Inc. Self stowing thrust reverser
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
US20080134664A1 (en) * 2006-12-06 2008-06-12 Spirit Aerosystems, Inc. Thrust reverser pin lock
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US7735778B2 (en) 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8109466B2 (en) * 2008-06-23 2012-02-07 Rohr, Inc. Thrust reverser cascade assembly and AFT cascade ring with flow deflector portion
US20090314887A1 (en) * 2008-06-23 2009-12-24 Rohr, Inc. Thrust reverser cascade assembly and aft cascade ring with flow deflector portion
US20120023900A1 (en) * 2010-07-20 2012-02-02 Airbus Operations (S.A.S.) Aircraft nacelle
US9085369B2 (en) * 2010-07-20 2015-07-21 Airbus Operations S.A.S. Pivoting door for thrust reverser with stable intermediate position
US8925295B2 (en) 2010-09-23 2015-01-06 Airbus Operations Air discharging device for an aircraft double-flow turbine engine
CN103827473A (zh) * 2011-09-29 2014-05-28 埃尔塞乐公司 带有侧面开口的推力反向器门
CN103047048A (zh) * 2011-10-13 2013-04-17 罗尔股份有限公司 具有流向偏转架的反向推力装置叶栅组件
CN103047048B (zh) * 2011-10-13 2016-11-30 罗尔股份有限公司 具有流向偏转架的反向推力装置叶栅组件
US9086034B2 (en) * 2011-10-13 2015-07-21 Rohr, Inc. Thrust reverser cascade assembly with flow deflection shelf
US20130092755A1 (en) * 2011-10-13 2013-04-18 Michael Ray Aten Thrust Reverser Cascade Assembly With Flow Deflection Shelf
US20140027536A1 (en) * 2012-07-24 2014-01-30 Rohr, Inc. Translating cascades
US9068532B2 (en) * 2012-07-24 2015-06-30 Rohr, Inc. Translating sleeve thrust reverser with movable cascade
US9016040B2 (en) * 2012-11-30 2015-04-28 General Electric Company Thrust reverser system with translating-rotating cascade and method of operation
US20140150403A1 (en) * 2012-11-30 2014-06-05 General Electric Company Thrust reverser system with translating-rotating cascade and method of operation
US20160160799A1 (en) * 2014-11-06 2016-06-09 Rohr, Inc. Split sleeve hidden door thrust reverser
US10309343B2 (en) * 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
US11434850B2 (en) 2014-11-06 2022-09-06 Rohr, Inc. Split sleeve hidden door thrust reverser
US20170198659A1 (en) * 2016-01-13 2017-07-13 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10533519B2 (en) * 2016-01-13 2020-01-14 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10343786B2 (en) * 2017-06-28 2019-07-09 General Electric Company System and method of operating a ducted fan propulsion system during aircraft taxi
US11230994B2 (en) * 2017-07-26 2022-01-25 Short Brothers Plc Nacelle with thrust reverser
US10995701B2 (en) 2019-09-05 2021-05-04 Rohr, Inc. Translating sleeve thrust reverser assembly

Also Published As

Publication number Publication date
FR2776023A1 (fr) 1999-09-17
FR2776023B1 (fr) 2000-04-07
CA2265230A1 (fr) 1999-09-12
JPH11294260A (ja) 1999-10-26
WO1999046498A1 (fr) 1999-09-16
EP0942165A1 (de) 1999-09-15

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Owner name: HISPANO SUIZA AEROSTRUCTURES, FRANCE

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Effective date: 20040704

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Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362